Transient And Nonlinear Effects On High Speed, Vibratory, Thermoelastic Instability Phenomena. Part II Aerothermoelastic Applications

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Report Number: WADD TR 60-484 Part II
Author(s): Brunelle, Eugene J., Jr.
Corporate Author(s): Aeroelastic And Structures Research Laboratory, Massachusetts Institute of Technology
Laboratory: Flight Dynamics Laboratory
Date of Publication: 1960-12
Pages: 22
Contract: AF 33(616)-6185
DoD Project: 1370
DoD Task: 13478
Identifier: AD0266375

This report investigates the equations representing the dynamic, torsion-bending motion of a wing which is one major component of an ultra-high performance manned vehicle. Preliminary work required for this investigation is included as an integral part of the report. This preliminary work includes (1) the derivation of an exact two-dimensional linearized aerodynamic theory for an accelerating unsteady supersonic airfoil, (2) the re-derivation of "piston theory" aerodynamics for arbitrary motion, and (3) a derivation for the torsional stiffness loss of an aircraft wing that includes the effects of a specified time-dependent wall temperature due to the given flight mission and that includes the effects of mid-plane stretching.The computer studies consider "super X-15" type wing performing two specified flight missions and provide answers in the form of pitch and plunge impulse response time histories. The "exact" solutions are compared with two approximate solutions. The results of the comparisons indicate a quasi-steady aero-thermoelastic analysis is adequate for manned vehicles of the foreseeable future. This statement does not apply to the dynamic stability analysis (rigid-body) of these vehicles since their lower rigid-body frequencies permit a moderate to strong coupling between the governing equations and their time-varying coefficients.

Provenance: Lockheed Martin Missiles & Fire Control

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